Turbine engine and containment assembly for use in a turbine engine

1. A turbine engine defining an axial direction and a radial direction, the turbine engine comprising: an engine casing comprising: a shell; and an angel wing member comprising a base defined at said shell and a tip positioned distal from said base; and a backsheet extending over said angel wing member such that an angled region is defined in said backsheet at an interface with said tip, wherein said tip has a predetermined contour capable of mitigating stress concentrations in said angled region induced from said tip in the event said angel wing member is deflected in the radial direction away from said shell and towards said backsheet; wherein said tip is moveable relative to a bulkhead that is adjacent to said tip, said bulkhead extending in the radial direction between said backsheet and said shell.

2. The turbine engine in accordance with claim 1 , wherein said tip is contoured with a radius size of at least 0.01 inch.

3. The turbine engine in accordance with claim 2 , wherein said tip is contoured with a full radius defined between a first side and a second side of said angel wing member.

4. The turbine engine in accordance with claim 2 , wherein said tip is contoured with a half radius oriented towards said backsheet.

5. The turbine engine in accordance with claim 1 , wherein said tip is contoured with a chamfer oriented towards said backsheet.

6. The turbine engine in accordance with claim 1 , wherein said angel wing member is oriented obliquely relative to said shell such that a cavity is at least partially defined between said shell and said angel wing member.

7. The turbine engine in accordance with claim 6 further comprising:

a honeycomb structure positioned within said cavity, wherein said backsheet further extends over said honeycomb structure and across said angel wing member; and

a layer of containment material extending over said backsheet.

8. The turbine engine in accordance with claim 7 further comprising an array of rotor blades positioned radially inward from said engine casing, wherein said array of rotor blades and said layer of containment material are axially aligned relative to a centerline of the turbine engine.

9. The turbine engine in accordance with claim 1 , wherein said engine casing comprises a fan case.

10. A containment assembly for use in a turbine engine defining an axial direction and a radial direction, said containment assembly comprising: an engine casing comprising: a shell; and an angel wing member comprising a base defined at said shell and a tip positioned distal from said base; a honeycomb structure coupled to said shell; and a backsheet comprising a first portion extending across said angel wing member, a second portion extending across said honeycomb structure, and an angled region defined between said first portion and said second portion, wherein said angled region extends across said tip of said angel wing member, wherein said tip has an at least partially arcuate cross-sectional profile capable of mitigating stress concentrations in said angled region induced from said tip in the event said angel wing member is deflected in the radial direction away from said shell and towards said backsheet; wherein said tip is moveable relative to a bulkhead that is adjacent to said tip, said bulkhead extending in the radial direction between said backsheet and said shell.

11. The containment assembly in accordance with claim 10 further comprising a layer of containment material extending over said backsheet.

12. The containment assembly in accordance with claim 11 , wherein the containment material includes an aramid material.

13. The turbine engine in accordance with claim 10 , wherein said tip is contoured with a full radius defined between a first side and a second side of said angel wing member.

14. The turbine engine in accordance with claim 10 , wherein said tip is contoured with a half radius oriented towards said backsheet.

15. A method of forming a containment assembly for use in a turbine engine, said method comprising: coupling a honeycomb structure to an engine casing, wherein the engine casing includes a shell and an angel wing member including a base defined at the shell and a tip positioned distal from the base; coupling a backsheet to the angel wing member and the honeycomb structure, wherein the backsheet includes a first portion extending across the angel wing member, a second portion extending across the honeycomb structure, and an angled region defined therebetween and extending across the tip of the angel wing member; and shaping the tip of the angel wing member with a predetermined contour capable of mitigating stress concentrations formed in the angled region induced from the tip in the event said angel wing member is deflected in the radial direction away from said shell and towards said backsheet; wherein said tip is moveable relative to a bulkhead that is adjacent to said tip, said bulkhead extending in the radial direction between said backsheet and said shell.

16. The method in accordance with claim 15 , wherein contouring the tip of the angel wing member comprises contouring the tip with a radius size of at least 0.01 inch.

17. The method in accordance with claim 16 , wherein contouring the tip of the angel wing member comprises contouring the tip with a full radius defined between a first side and a second side of the angel wing member.

18. The method in accordance with claim 16 , wherein contouring the tip of the angel wing member comprises contouring the tip with a half radius oriented towards said backsheet.

19. The method in accordance with claim 17 further comprising extending a layer of containment material across the backsheet.

20. The turbine engine in accordance with claim 1 , wherein said tip is moveable within a notch of the bulkhead.